FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 03-182 AIRFOIL (fxs03182-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.3 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs03182-il-1000000-n5.txt Download as CSV file: xf-fxs03182-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 03-182 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.4215 0.12934 0.12741 -0.0694 0.9464 0.0019
-16.250 -0.4818 0.11011 0.10803 -0.0772 0.9457 0.0018
-16.000 -0.5181 0.09452 0.09223 -0.0867 0.9409 0.0018
-15.750 -0.5312 0.08229 0.07979 -0.0977 0.9339 0.0017
-15.500 -0.5405 0.07110 0.06834 -0.1095 0.9258 0.0017
-15.250 -0.5417 0.06132 0.05821 -0.1217 0.9080 0.0017
-15.000 -0.5455 0.05516 0.05172 -0.1279 0.8801 0.0017
-14.750 -0.5515 0.05121 0.04751 -0.1298 0.8548 0.0017
-14.500 -0.5548 0.04814 0.04425 -0.1308 0.8366 0.0017
-14.250 -0.5592 0.04515 0.04108 -0.1313 0.8218 0.0017
-14.000 -0.5648 0.04223 0.03797 -0.1315 0.8084 0.0017
-13.500 -0.5683 0.03749 0.03290 -0.1311 0.7864 0.0017
-13.250 -0.5678 0.03550 0.03075 -0.1306 0.7774 0.0017
-13.000 -0.5646 0.03377 0.02889 -0.1300 0.7691 0.0017
-12.750 -0.5627 0.03194 0.02691 -0.1292 0.7618 0.0017
-12.500 -0.5576 0.03042 0.02526 -0.1284 0.7543 0.0017
-12.250 -0.5542 0.02875 0.02345 -0.1272 0.7479 0.0018
-12.000 -0.5432 0.02778 0.02238 -0.1266 0.7413 0.0017
-11.750 -0.5355 0.02651 0.02099 -0.1256 0.7355 0.0017
-11.500 -0.5256 0.02542 0.01981 -0.1246 0.7295 0.0017
-11.000 -0.5047 0.02340 0.01760 -0.1225 0.7186 0.0018
-10.750 -0.4937 0.02244 0.01655 -0.1213 0.7131 0.0018
-10.500 -0.4828 0.02152 0.01555 -0.1200 0.7082 0.0018
-10.250 -0.4697 0.02073 0.01469 -0.1190 0.7036 0.0018
-10.000 -0.4581 0.01988 0.01376 -0.1177 0.6989 0.0018
-9.750 -0.4452 0.01916 0.01297 -0.1164 0.6948 0.0018
-9.500 -0.4313 0.01846 0.01222 -0.1153 0.6912 0.0018
-9.250 -0.4188 0.01772 0.01141 -0.1139 0.6874 0.0019
-9.000 -0.4042 0.01714 0.01078 -0.1127 0.6837 0.0019
-8.500 -0.3781 0.01588 0.00942 -0.1097 0.6775 0.0019
-8.250 -0.3655 0.01529 0.00879 -0.1080 0.6744 0.0019
-8.000 -0.3544 0.01481 0.00827 -0.1060 0.6713 0.0020
-7.750 -0.3457 0.01427 0.00768 -0.1036 0.6683 0.0020
-7.500 -0.3324 0.01366 0.00699 -0.1020 0.6655 0.0022
-7.250 -0.3129 0.01327 0.00656 -0.1012 0.6631 0.0022
-7.000 -0.2922 0.01291 0.00616 -0.1006 0.6603 0.0023
-6.750 -0.2708 0.01256 0.00578 -0.1000 0.6576 0.0026
-6.500 -0.2479 0.01228 0.00546 -0.0996 0.6550 0.0026
-6.250 -0.2247 0.01200 0.00514 -0.0993 0.6527 0.0030
-6.000 -0.2004 0.01174 0.00484 -0.0992 0.6507 0.0031
-5.750 -0.1751 0.01151 0.00458 -0.0991 0.6487 0.0035
-5.500 -0.1494 0.01129 0.00434 -0.0992 0.6467 0.0036
-5.250 -0.1239 0.01104 0.00406 -0.0992 0.6446 0.0041
-5.000 -0.0978 0.01082 0.00381 -0.0993 0.6426 0.0047
-4.750 -0.0714 0.01062 0.00358 -0.0995 0.6407 0.0064
-4.500 -0.0449 0.01043 0.00341 -0.0997 0.6388 0.0144
-4.250 -0.0176 0.01032 0.00329 -0.0999 0.6371 0.0159
-4.000 0.0100 0.01015 0.00313 -0.1003 0.6356 0.0183
-3.750 0.0379 0.01001 0.00299 -0.1007 0.6341 0.0199
-3.500 0.0660 0.00990 0.00287 -0.1011 0.6324 0.0206
-3.250 0.0941 0.00979 0.00276 -0.1015 0.6306 0.0236
-3.000 0.1220 0.00962 0.00264 -0.1019 0.6288 0.0362
-2.750 0.1503 0.00953 0.00254 -0.1023 0.6272 0.0429
-2.500 0.1784 0.00938 0.00244 -0.1028 0.6257 0.0605
-2.250 0.2065 0.00915 0.00232 -0.1034 0.6243 0.0989
-1.750 0.2663 0.00699 0.00158 -0.1073 0.6218 0.5232
-1.500 0.2962 0.00697 0.00160 -0.1080 0.6206 0.5471
-1.250 0.3259 0.00697 0.00163 -0.1086 0.6194 0.5586
-1.000 0.3555 0.00699 0.00164 -0.1092 0.6181 0.5662
-0.750 0.3850 0.00700 0.00167 -0.1098 0.6168 0.5735
-0.500 0.4145 0.00704 0.00170 -0.1104 0.6153 0.5817
-0.250 0.4437 0.00708 0.00175 -0.1109 0.6129 0.5903
0.000 0.4723 0.00715 0.00178 -0.1112 0.6093 0.5950
0.250 0.5013 0.00714 0.00178 -0.1117 0.6042 0.5963
0.500 0.5302 0.00716 0.00181 -0.1122 0.6004 0.5985
0.750 0.5590 0.00721 0.00185 -0.1126 0.5972 0.6020
1.000 0.5875 0.00728 0.00190 -0.1129 0.5943 0.6056
1.250 0.6167 0.00730 0.00193 -0.1134 0.5910 0.6079
1.750 0.6720 0.00738 0.00196 -0.1139 0.5695 0.6100
2.000 0.6997 0.00744 0.00200 -0.1141 0.5601 0.6113
2.250 0.7261 0.00754 0.00206 -0.1140 0.5431 0.6126
2.500 0.7471 0.00787 0.00219 -0.1130 0.4977 0.6138
2.750 0.7322 0.00993 0.00328 -0.1056 0.3031 0.6150
3.000 0.7327 0.01108 0.00396 -0.1010 0.1983 0.6162
3.250 0.7344 0.01193 0.00448 -0.0965 0.1248 0.6175
3.500 0.7429 0.01248 0.00487 -0.0933 0.0847 0.6187
3.750 0.7553 0.01299 0.00527 -0.0908 0.0536 0.6200
4.000 0.7737 0.01332 0.00556 -0.0894 0.0454 0.6212
4.250 0.7905 0.01371 0.00590 -0.0879 0.0336 0.6223
4.750 0.8284 0.01434 0.00654 -0.0856 0.0272 0.6250
5.000 0.8469 0.01468 0.00690 -0.0844 0.0236 0.6266
5.250 0.8611 0.01522 0.00742 -0.0826 0.0134 0.6282
5.500 0.8781 0.01567 0.00787 -0.0813 0.0122 0.6297
5.750 0.8949 0.01614 0.00835 -0.0800 0.0104 0.6312
6.000 0.9123 0.01661 0.00884 -0.0789 0.0096 0.6328
6.250 0.9297 0.01709 0.00934 -0.0778 0.0092 0.6344
6.500 0.9468 0.01761 0.00988 -0.0768 0.0082 0.6359
6.750 0.9628 0.01821 0.01049 -0.0756 0.0061 0.6374
7.000 0.9763 0.01896 0.01125 -0.0741 0.0021 0.6389
7.250 0.9924 0.01960 0.01192 -0.0731 0.0019 0.6407
7.500 1.0079 0.02029 0.01265 -0.0720 0.0018 0.6426
7.750 1.0229 0.02103 0.01343 -0.0709 0.0017 0.6447
8.000 1.0378 0.02180 0.01424 -0.0698 0.0016 0.6470
8.250 1.0526 0.02260 0.01508 -0.0688 0.0016 0.6491
8.500 1.0667 0.02346 0.01598 -0.0677 0.0015 0.6512
9.000 1.0944 0.02527 0.01787 -0.0657 0.0014 0.6552
9.250 1.1076 0.02625 0.01891 -0.0646 0.0014 0.6576
9.500 1.1194 0.02735 0.02007 -0.0635 0.0013 0.6600
9.750 1.1318 0.02841 0.02118 -0.0625 0.0012 0.6625
10.000 1.1430 0.02960 0.02244 -0.0614 0.0011 0.6650
10.250 1.1555 0.03072 0.02360 -0.0605 0.0011 0.6674
10.500 1.1680 0.03186 0.02480 -0.0597 0.0011 0.6701
10.750 1.1808 0.03298 0.02598 -0.0589 0.0011 0.6730
11.000 1.1925 0.03423 0.02728 -0.0581 0.0011 0.6760
11.250 1.2042 0.03551 0.02861 -0.0573 0.0011 0.6791
11.500 1.2158 0.03682 0.02998 -0.0565 0.0010 0.6821
11.750 1.2270 0.03818 0.03140 -0.0558 0.0010 0.6855
12.000 1.2377 0.03962 0.03291 -0.0551 0.0010 0.6893
12.250 1.2483 0.04109 0.03446 -0.0544 0.0010 0.6932
12.500 1.2588 0.04260 0.03603 -0.0538 0.0009 0.6967
12.750 1.2689 0.04418 0.03768 -0.0533 0.0009 0.7005
13.000 1.2790 0.04578 0.03935 -0.0527 0.0009 0.7046
13.250 1.2876 0.04756 0.04120 -0.0522 0.0009 0.7087
13.500 1.2975 0.04924 0.04295 -0.0518 0.0009 0.7128
13.750 1.3052 0.05120 0.04499 -0.0513 0.0008 0.7173
14.000 1.3134 0.05313 0.04700 -0.0509 0.0008 0.7223
14.500 1.3275 0.05733 0.05139 -0.0503 0.0008 0.7320
14.750 1.3338 0.05959 0.05373 -0.0501 0.0008 0.7375
15.000 1.3402 0.06188 0.05611 -0.0499 0.0007 0.7428
15.250 1.3452 0.06438 0.05871 -0.0499 0.0007 0.7486
15.500 1.3493 0.06704 0.06147 -0.0499 0.0007 0.7545
15.750 1.3535 0.06973 0.06426 -0.0500 0.0007 0.7605
16.000 1.3566 0.07263 0.06727 -0.0501 0.0007 0.7672
16.250 1.3592 0.07566 0.07041 -0.0504 0.0006 0.7739
16.500 1.3606 0.07891 0.07377 -0.0509 0.0006 0.7813
16.750 1.3614 0.08231 0.07729 -0.0514 0.0006 0.7886
17.000 1.3612 0.08591 0.08101 -0.0521 0.0006 0.7967
17.250 1.3592 0.08989 0.08512 -0.0529 0.0006 0.8044
17.500 1.3577 0.09386 0.08922 -0.0540 0.0006 0.8132
17.750 1.3543 0.09823 0.09373 -0.0552 0.0006 0.8227
18.000 1.3496 0.10287 0.09851 -0.0567 0.0005 0.8329
18.250 1.3444 0.10768 0.10347 -0.0584 0.0005 0.8449
18.500 1.3384 0.11272 0.10866 -0.0603 0.0005 0.8591
18.750 1.3299 0.11817 0.11430 -0.0624 0.0005 0.8772
19.000 1.3205 0.12336 0.11968 -0.0642 0.0005 0.9114
19.250 1.3085 0.12817 0.12467 -0.0653 0.0005 1.0000
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Polar data table (+)
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